FR3094398B1 - Ensemble pour un rotor de turbomachine - Google Patents

Ensemble pour un rotor de turbomachine Download PDF

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Publication number
FR3094398B1
FR3094398B1 FR1903333A FR1903333A FR3094398B1 FR 3094398 B1 FR3094398 B1 FR 3094398B1 FR 1903333 A FR1903333 A FR 1903333A FR 1903333 A FR1903333 A FR 1903333A FR 3094398 B1 FR3094398 B1 FR 3094398B1
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FR
France
Prior art keywords
disc
flange
bolt
upstream
branch
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR1903333A
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English (en)
Other versions
FR3094398A1 (fr
Inventor
Kevin Eugène Henri Giboudeaux
Pascal Michel Noël Lefebvre
Hadrien Paul Alexandre Mage
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1903333A priority Critical patent/FR3094398B1/fr
Publication of FR3094398A1 publication Critical patent/FR3094398A1/fr
Application granted granted Critical
Publication of FR3094398B1 publication Critical patent/FR3094398B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne un ensemble pour un rotor (1) d’une turbomachine s’étendant selon un axe, comportant un disque (2) annulaire s’étendant radialement, au moins une virole (9) amont ou aval, comportant une bride (10) en appui sur une face amont ou aval du disque (2), ladite bride (10) étant fixée au disque (2) par l’intermédiaire d’au moins un boulon (13), le boulon (13) comportant une vis (16) coopérant avec un écrou (18), caractérisé en ce que ledit ensemble comporte au moins un organe de déflection (23) présentant une forme générale en U comprenant une base (24) radialement externe à partir de laquelle une branche amont (25) et une branche aval (26) s’étendent radialement vers l’intérieur, l’une (26) desdites branches (25, 26) étant fixée à la bride (10) et au disque (2) par l’intermédiaire du boulon (13), ladite branche (26) comportant au moins une ouverture (27) de fixation traversée par la vis (16). Figure à publier avec l’abrégé : Figure 2
FR1903333A 2019-03-29 2019-03-29 Ensemble pour un rotor de turbomachine Active FR3094398B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1903333A FR3094398B1 (fr) 2019-03-29 2019-03-29 Ensemble pour un rotor de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1903333A FR3094398B1 (fr) 2019-03-29 2019-03-29 Ensemble pour un rotor de turbomachine
FR1903333 2019-03-29

Publications (2)

Publication Number Publication Date
FR3094398A1 FR3094398A1 (fr) 2020-10-02
FR3094398B1 true FR3094398B1 (fr) 2021-03-12

Family

ID=67107890

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1903333A Active FR3094398B1 (fr) 2019-03-29 2019-03-29 Ensemble pour un rotor de turbomachine

Country Status (1)

Country Link
FR (1) FR3094398B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021123173A1 (de) * 2021-09-07 2023-03-09 MTU Aero Engines AG Rotorscheibe mit gekrümmtem Rotorarm für eine Fluggasturbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2570764B1 (fr) * 1984-09-27 1986-11-28 Snecma Dispositif de controle automatique du jeu d'un joint a labyrinthe de turbomachine
FR2607866B1 (fr) 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
US5562404A (en) * 1994-12-23 1996-10-08 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes
FR2856755B1 (fr) * 2003-06-26 2007-03-23 Snecma Moteurs Dispositif de fixation par vis et ecrous
US20120003091A1 (en) * 2010-06-30 2012-01-05 Eugenio Yegro Segovia Rotor assembly for use in gas turbine engines and method for assembling the same
US9045990B2 (en) * 2011-05-26 2015-06-02 United Technologies Corporation Integrated ceramic matrix composite rotor disk geometry for a gas turbine engine

Also Published As

Publication number Publication date
FR3094398A1 (fr) 2020-10-02

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